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Ocean momentum and energy transfer parameters on a nearly all weather operational basis are obtained and used. The winds, water vapor, liquid water content, temperature, and mean cloud droplet size are derived from low altitude parameters.
Airborne in situ exhaust cloud measurements were conducted to obtain definitions of cloud particle size range, Cl2 content, and HCl partitioning. Particle size distribution data and Cl2 measurements were made during the May, August, and September 1977 Titan launches. The measurements of three basic effluents - HCl, NO sub X, and particles - against minutes after launch are plotted. The maximum observed HCl concentration to the maximum Cl2 concentration are compared and the ratios of the Cl2 to the HCl is calculated.
The performance of an aircraft in various measured icing conditions was investigated. Icing parameters such as liquid water content, temperature, cloud droplet sizes and distributions were measured continuously while in icing. Flight data were reduced to provide plots of the aircraft drag polars and lift curves (CL vs. alpha) for the measured ""iced'' condition as referenced to the uniced aircraft. These data were also reduced to provide plots of thrust horsepower required vs. single engine power available to show how icing affects engine out capability. It is found that performance degradation is primarily influenced by the amount and shape of the accumulated ice. Glaze icing caused the greatest aerodynamic performance penalties in terms of increased drag and reduction in lift while aerodynamic penalties due to rime icing were significantly lower.
The performance of an aircraft in various measured icing conditions was investigated. Icing parameters such as liquid water content, temperature, cloud droplet sizes and distributions were measured continuously while in icinig. Flight data wre reduced to provide plots of the aircraft drag polars and lift curves (CL vs. alpha) for the measured 'iced' condition as referenced to the uniced aircraft. These data were also reduced to provide plots of thrust horsepower required vs. single engine power available to show how icing affects engine out capability. It is found that performance degradation is primarily influenced by the amount and shape of the accumulated ice. Glaze icing caused the greatest aerodynamic performance penalties in terms of increased drag and reduction in lift while aerodynamic penalties due to rime icing were significantly lower. Previously announced in STAR as N84-13173
The evidence for solid mode 3 particles in the clouds of Venus is reexamined. The sampling characteristics of the cloud particle size spectrometer (LCPS) are reviewed, and reasons are pointed out for believing that relatively small differences in interpreting the measurements of this instrument could produce systematic errors. It is shown that all of the Pioneer Venus and Venera measurements can be understood if it is assumed that the large particles observed by the LCPS form the tail of the mode 2, H2SO4 size distribution.
The structural properties of ice accretions formed on aircraft surfaces are studied. The overall objectives are to measure basic structural properties of impact ices and to develop finite element analytical procedures for use in the design of all deicing systems. The Icing Research Tunnel (IRT) was used to produce simulated natural ice accretion over a wide range of icing conditions. Two different test apparatus were used to measure each of the three basic mechanical properties: tensile, shear, and peeling. Data was obtained on both adhesive shear strength of impact ices and peeling forces for various icing conditions. The influences of various icing parameters such as tunnel air temperature and velocity, icing cloud drop size, material substrate, surface temperature at ice/material interface, and ice thickness were studied. A finite element analysis of the shear test apparatus was developed in order to gain more insight in the evaluation of the test data. A comparison with other investigators was made. The result shows that the adhesive shear strength of impact ice typically varies between 40 and 50 psi, with peak strength reaching 120 psi and is not dependent on the kind of substrate used, the thickness of accreted ice, and tunnel temperature below 4 C.
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The IR and H I properties and CO content of a set of 26 isolated, roughly degree-sized interstellar clouds are compared. It is argued that G230.1-28.4, the cloud with the narrowest H I line, has recently been shocked by the same collision that a neighboring cloud, G228.0-28.6, is currently undergoing. The ratio S(100)/N(H I) is found to range up to much larger values than predicted theoretically, where N(H) represents the column density of H nuclei and S(100) is the 100 micron surface brightness. Clouds with the highest such values are observed to contain CO, and it is inferred that they contain H2. The (H2/H I) ratio of a cloud increases as the measure of its internal velocity differences decreases. The dependence of S(60)/S(100) on V(LSR) implies that fast shocks preferentially destroy large grains or produce small grains, or both.
Data collected during flight 9 of the Stratosphere-Troposphere Exchange Project (STEP), in Australia (1987), are used in an attempt to define the nature of one particular cirrus outflow region and its radiative impact. To explore the mechanisms by which air is exchanged between the stratosphere and troposphere, a series of instruments was flown on the NASA ER-2 high-altitude research aircraft to make measurements relevant to the radiative budget of tropical clouds. The data acquired included upwelling infrared radiance at 10.5 and 6.5 microns (spectral bandwidth of 1 micron); net infrared flux (spectral bandwidth of 3 to 40 microns); cloud particle size distribution; water-vapor and total water (vapor plus condensed phase); aerosol particle size distribution; and ambient temperature.
Researchers briefly review the diffusion domain method for deriving the cloud similarity parameter and present preliminary analyses of the results thus far obtained. The presentation concentrates on the following points: (1) intercomparison of calibrated reflected intensities between the cloud absorption radiometer and the U.K. multispectral cloud radiometer; (2) quality control tests required to select those portions of an aircraft flight for which measurements are obtained within the diffusion domain; (3) case studies of the spectral similarity parameter of marine stratocumulus clouds; and comparisons of the experimentally-derived similarity parameter spectrum with that expected theoretically from the cloud droplet size distribution obtained from in situ observations.
A scattered-light scanning instrument developed at NASA Lewis Research Center was used to measure the characteristic drop size of clouds of liquid nitrogen droplets. The instrument was calibrated with suspensions of monosized polystyrene spheres. In this investigation of the mechanism of liquid nitrogen jet disintegration in a high-velocity gas flow, the Sauter mean diameter, D32, was found to vary inversely with the nitrogen gas mass flux raised to the power 1.33. Values of D32 varied from 5 to 25 microns and the mass flux exponent of 1.33 agrees well with theory for liquid jet breakup in high-velocity gas flows. The loss of very small droplets due to the high vaporization rate of liquid nitrogen was avoided by sampling the spray very close to the atomizer, i.e., 1.3 cm downstream of the nozzle orifice. The presence of high velocity and thermal gradients in the gas phase also made sampling of the particles difficult. As a result, it was necessary to correct the measurements for background noise produced by both highly turbulent gas flows and thermally induced density gradients in the gas phase.
Results are presented of an application of the diffusion domain method to multispectral solar radiation measurements obtained deep within a marine stratocumulus cloud layer modified by pollution from ships. In situ airborne measurements of the relative angular distribution of scattered radiation are compared to known asymptotic expressions for the intensity field deep within an optically thick cloud layer. Analytical expressions relating the ratio of the nadir-to-zenith intensities to surface reflectance, similarity parameter, and scaled optical depth beneath the aircraft flight level are used to analyze measurements obtained with the cloud absorption radiometer mounted on the University of Washington's C-131A research aircraft. It is shown that the total optical thickness of the cloud layer increased in the ship tracks, in contrast to the similarity parameter, which decreased. The decrease in absorption was a direct consequence of the reduction in cloud droplet size that occurred within the ship tracks.
The region of the IR spectrum that is ideally suited for detecting optically thin cirrus clouds is in the window between 10 and 13 microns. Here relatively weak absorption due to the water vapor lines and continuum is present and hence the extinction characteristic of the cloud particles is readily discernible. In order to demonstrate these properties, two IR spectra are presented, one with clear skies and one with an optically thin cirrus. As a result of the cloud particle extinction, an appreciable increase in the brightness temperature from 10 to 13 microns is observed. This decrease is found to be nearly linear in the case of the tropical thin cirrus, which is also geometrically thin. On the basis of radiative transfer simulations, it is inferred that the cloud particle size that can produce this spectral character has an effective diameter of about 12 microns, which is comparable to the wavelength of the radiation.
The use of the Advanced Microwave Sounding Unit (AMSU) moisture imagery for the dynamic, kinematic, and synoptic interpretations requires the availability of idealized 'soundings' of temperature, water vapor, and cloudiness as input to a radiative transfer model for determining how atmospheric conditions control the top-of-atmosphere brightness temperatures. This paper uses idealized vertical configurations of atmospheric water vapor and liquid cloud water to illustrate their effects on the AMSU moisture channels. Calculations with various cloud-drop size distribution functions (SDFs) showed that, at least for the specific SDFs used in this work, the Rayleigh approximation is invalid for mode radii greater than 30-40 microns, for frequencies above 89.0 GHz. It is also invalid above about 20 microns for frequencies above 157 GHz. It is concluded that AMSU moisture channels might not be suitable for detecting convective instability over land using image-based approaches.
If gravitational clustering is a hierarchical process, the present large-scale structure of the galaxy distribution implies that structures on smaller scales must have formed at high redshift. We simulate the formation of small-scale structure (average cell mass: (delta) bar m(sub b) = 10(sup 4.2) solar mass) and the evolution of photoionized gas, in the specific case of the CDM + Lambda model. The photoionized gas has a natural minimal scale of collapse, the Jeans scale (m(sub b,J) is approximately equal to 10(exp 9) solar mass). We find that low column density (N(sub HI) is less than or equal to 10(exp 14)/sq cm) lines originate in regions resembling Zel'dovich pancakes, where gas with overdensities in the range 3-30 is enclosed by two shocks but is typically reexpanding at approximately the Hubble velocity. However, higher column density lines stem from more overdense regions where the shocked gas is cooling. We show that this model can probably account for the observed number of lines, their distribution in column density and b-parameters, as well as the cloud physical sizes as observed in gravitationally lensed quasars. We find a redshift evolution that is too steep; however, this may be due to insufficient dynamical range in the simulation or because the specific model is incorrect. The model predicts that high signal-to-noise observations should find systematic deviations from Voigt profiles, mainly in the form of broad wings in the line profiles, and that a fluctuating Gunn-Peterson effect will be detected, which can be modeled as a superposition of weak lines with a wide range of b-parameters.
Improvements in the remote sensing of clouds from space in the future will come from instruments with higher spatial and spectral resolution on more platforms and supported by active sounding. The space shuttle hitchhiker system allows new measurements to be prototyped in space with costs, operating flexibility and data volumes similar to aircraft experiments. The Infrared Spectral Imaging Radiometer and Shuttle Laser Altimeter hitchhiker experiment was flown in 1997. The experiment tested the use of uncooled thermal infrared imaging, laser cloud altitude measurements and high spatial resolution, tri-spectral sensing of cloud particle size and phase. A 1/4 km resolution, fifty orbit data set was obtained from STS-85. The presentation will focus on the use of the shuttle as an experiment platform and cover possible transition to the space station in the future.
The degree to which water ice clouds play a role in the Mars climate is unknown. Latent heating of water ice clouds is small and since most hazes appeared to be thin (tau less than or = 1) their radiative effects have been neglected. Condensation likely limits the vertical extent of water vapor in the water column and a lowering of the condensation altitude, as seen in the northern spring and summer, could increase the seasonal exchange of water between the atmosphere and the surface. It has been suggested that water ice cloud formation is more frequent and widespread in the aphelic hemisphere (currently the northern). This may limit water to the northern hemisphere through greater exchange with the regolith and through restricted southward transport of water vapor by the Mars Hadley circulation. In addition, it has been suggested that water ice cloud formation also controls the vertical distribution of atmospheric dust in some seasons. This scavenging of dust may Continuing from the IRTM cloud maps, derived cloud opacities and cloud temperatures for several locations and seasons will be presented. Sensitivities to cloud particle sizes, surface temperature, and dust opacity will be discussed.
The Surface Heat and Energy Budget of the Arctic (SHEBA) was an intensive field project which took place in the Arctic Ocean from October 1997 through October 1998. Its purpose was to measure as many facets of the Arctic environment as possible so that we would be able to better understand the interaction between the ice, atmosphere, and ocean and their interactions with global climate. One aspect of the atmospheric field component was launching tethered balloons to monitor the profiles of temperature, wind, pressure, and humidity, as well as examine the vertical structure of cloud droplet sizes and distributions. The tethered balloon that we used was one specially designed for use in freezing climates by SPEC Corporation in Boulder, Colorado. A special winch that was able to withstand Arctic temperature and weather became necessary when the testing of simple winch systems used in warmer climates failed under these extreme conditions. The purpose of this manual is to acquaint any new user to the powered tethered balloon system deployed at the The Surface Heat and Energy Budget of the Arctic (SHEBA ice camp. It includes a description of the preparations necessary to get ready for a launch, the mechanics of the actual launch, and an account of the proper procedure for taking down the equipment when finished. It will also include tips on how to minimize potential equipment failures, some trouble shooting, and some safety ideas. This manual is designed so that new operators can use the system with minimal previous training. At the end of this manual, the reader will find a quick checklist.